function engine_load(ISA)

% % %%%%%%%%%%%%% Function TestBed %%%%%%%%%%%%%%%
% % clc
% % clear all
% % close all
% % ISA=0;% Test
% % %%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%%

%SI units

%Add path for selected ISA conditions
addpath(strcat('engine_','ISA_',num2str(ISA)));

%% Compute altitude and airspeed ranges

%Read simulation output - Mach and altitude range purposes
[a,b,c] = xlsread(strcat('output_0.xls'));

%Read mach number range
M_range=a(3,:);

%Read altitude range
d=1;
for i=2:10:(size(a,1)-6)
alt_range(d)=a(i,1);
d=d+1;
end

%% Define TSFC and T matrixes

k=1;
for throttle = 0:10:100 %Throttle lever position - k index

%Read engine simulation output 
[a,b,c] = xlsread(strcat('output_' , num2str(throttle) , '.xls'));

%Compute TSFC for throttle k - [g/N.s]
v=1;
for j=1:1:size(alt_range,2)
    for i=1:1:size(M_range,2)
        TSFC_matrix(j,i,k) = a(v+6,i,1)/1000;
    end
    v=v+10;
end

% TSFC=TSFC.*((3600*9.81)/1e6) %TSFC in [kg/kgf.h]

%Compute Thrust for throttle k - Newtons
v=1;
for j=1:1:size(alt_range,2)
    for i=1:1:size(M_range,2)
        T_matrix(j,i,k) = a(v+7,i,1).*1000;
    end
    v=v+10;
end

th_range(k)=throttle;
k=k+1;
end

th_range=th_range';

%Saves engine parameters in the workspace
save('engine','TSFC_matrix','T_matrix','th_range','M_range','alt_range'); 